NACA M8 AIRFOIL (m8-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M8 AIRFOIL (m8-il) Reynolds number: 100,000 Max Cl/Cd: 40.38 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m8-il-100000.txt Download as CSV file: xf-m8-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M8 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1491 0.11029 0.10608 -0.0236 0.8639 0.0787
-9.000 -0.1541 0.11107 0.10684 -0.0262 0.8474 0.0801
-8.750 -0.1667 0.11283 0.10860 -0.0291 0.8323 0.0805
-8.500 -0.1343 0.10346 0.09915 -0.0251 0.8192 0.0823
-8.250 -0.1235 0.10071 0.09635 -0.0244 0.8057 0.0848
-8.000 -0.1172 0.09866 0.09423 -0.0243 0.7945 0.0875
-7.750 -0.1124 0.09698 0.09255 -0.0254 0.7830 0.0903
-7.500 -0.1216 0.09805 0.09364 -0.0283 0.7733 0.0921
-7.250 -0.1216 0.09741 0.09300 -0.0325 0.7642 0.0928
-7.000 -0.0996 0.09081 0.08634 -0.0280 0.7566 0.0945
-6.750 -0.0863 0.08803 0.08355 -0.0277 0.7474 0.0971
-6.500 -0.0780 0.08614 0.08160 -0.0282 0.7407 0.1009
-6.250 -0.0712 0.08827 0.08371 -0.0396 0.7314 0.1053
-6.000 -0.0590 0.08233 0.07776 -0.0342 0.7250 0.1068
-5.750 -0.0441 0.07946 0.07490 -0.0335 0.7169 0.1095
-5.500 -0.0301 0.07738 0.07278 -0.0347 0.7093 0.1138
-5.250 -0.0122 0.07636 0.07166 -0.0419 0.7025 0.1186
-5.000 0.0011 0.07288 0.06822 -0.0393 0.6940 0.1211
-4.750 0.0220 0.07185 0.06704 -0.0433 0.6877 0.1293
-4.500 0.0378 0.06873 0.06398 -0.0433 0.6789 0.1320
-4.250 0.0560 0.06666 0.06184 -0.0437 0.6721 0.1376
-3.750 0.0988 0.06252 0.05760 -0.0475 0.6568 0.1477
-3.500 0.1232 0.06049 0.05541 -0.0500 0.6514 0.1531
-3.000 0.1724 0.05657 0.05137 -0.0537 0.6356 0.1635
-2.750 0.1953 0.05464 0.04940 -0.0544 0.6280 0.1679
-2.500 0.2325 0.05345 0.04797 -0.0592 0.6200 0.1726
-2.250 0.2499 0.05062 0.04506 -0.0579 0.6151 0.1748
-2.000 0.2761 0.04893 0.04337 -0.0593 0.6051 0.1783
-1.750 0.3058 0.04705 0.04127 -0.0607 0.5991 0.1802
-1.500 0.3346 0.04531 0.03941 -0.0624 0.5911 0.1798
-1.250 0.3732 0.04125 0.03493 -0.0665 0.5846 0.1494
-1.000 0.4134 0.03489 0.02774 -0.0703 0.5807 0.1299
-0.750 0.4362 0.03540 0.02841 -0.0695 0.5722 0.1340
-0.500 0.4670 0.03340 0.02602 -0.0701 0.5661 0.1402
-0.250 0.4929 0.03298 0.02547 -0.0690 0.5616 0.1456
0.000 0.5195 0.03283 0.02529 -0.0691 0.5520 0.1550
0.250 0.5473 0.03216 0.02439 -0.0682 0.5460 0.1664
0.500 0.5754 0.03189 0.02390 -0.0679 0.5383 0.1837
0.750 0.5997 0.03166 0.02365 -0.0671 0.5306 0.2009
1.000 0.6270 0.03092 0.02259 -0.0662 0.5257 0.2306
1.250 0.6496 0.03066 0.02239 -0.0659 0.5165 0.2589
1.500 0.6748 0.02970 0.02126 -0.0651 0.5106 0.2913
1.750 0.7017 0.02907 0.02036 -0.0644 0.5059 0.3224
2.000 0.7241 0.02889 0.02027 -0.0642 0.4978 0.3436
2.250 0.7510 0.02844 0.01965 -0.0636 0.4923 0.3603
2.500 0.7783 0.02851 0.01952 -0.0631 0.4870 0.3707
2.750 0.8015 0.02857 0.01968 -0.0629 0.4791 0.3826
3.000 0.8291 0.02819 0.01917 -0.0624 0.4739 0.3950
3.250 0.8555 0.02838 0.01928 -0.0621 0.4680 0.3990
3.500 0.8806 0.02865 0.01958 -0.0618 0.4602 0.3963
3.750 0.9106 0.02836 0.01908 -0.0614 0.4551 0.3913
4.000 0.9344 0.02901 0.01974 -0.0610 0.4470 0.3866
4.250 0.9620 0.02883 0.01950 -0.0606 0.4402 0.3841
4.500 0.9906 0.02863 0.01916 -0.0602 0.4347 0.3822
4.750 1.0134 0.02912 0.01976 -0.0598 0.4255 0.3800
5.000 1.0451 0.02876 0.01919 -0.0596 0.4200 0.3764
5.250 1.0673 0.02942 0.01996 -0.0592 0.4103 0.3731
5.500 1.0977 0.02916 0.01950 -0.0588 0.4038 0.3700
5.750 1.1214 0.02965 0.02008 -0.0586 0.3941 0.3681
6.000 1.1523 0.02936 0.01963 -0.0585 0.3870 0.3658
6.250 1.1743 0.03002 0.02038 -0.0580 0.3775 0.3639
6.500 1.2030 0.03000 0.02022 -0.0578 0.3706 0.3618
6.750 1.2241 0.03082 0.02113 -0.0572 0.3625 0.3601
7.000 1.2485 0.03124 0.02151 -0.0567 0.3554 0.3585
7.250 1.2761 0.03160 0.02172 -0.0563 0.3500 0.3572
7.500 1.2902 0.03292 0.02328 -0.0553 0.3423 0.3562
7.750 1.3160 0.03325 0.02355 -0.0549 0.3371 0.3554
8.000 1.3385 0.03404 0.02432 -0.0543 0.3321 0.3556
8.250 1.3491 0.03553 0.02606 -0.0530 0.3259 0.3560
8.500 1.3707 0.03617 0.02671 -0.0523 0.3213 0.3569
8.750 1.3997 0.03654 0.02697 -0.0521 0.3179 0.3580
9.000 1.4044 0.03869 0.02940 -0.0507 0.3136 0.3584
9.250 1.4069 0.04089 0.03186 -0.0491 0.3093 0.3586
9.500 1.4181 0.04243 0.03351 -0.0480 0.3058 0.3588
9.750 1.4392 0.04333 0.03443 -0.0474 0.3030 0.3594
10.000 1.4698 0.04387 0.03490 -0.0474 0.3006 0.3606
10.250 1.4249 0.04938 0.04085 -0.0438 0.2975 0.3597
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Polar data table (+)
Polar graphs
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